发明名称 |
Cooled turbine blade tip closure |
摘要 |
An improved high pressure turbine rotor blade and tip cap structure therefor is provided, which comprises, a plurality of metallic layers bonded to the tip end of the blade, each layer having a peipheral shape conforming to the camber of the blade, the layers defining a plurality of radially outwardly opening, serpentine-shaped passageways for passage of coolant fluid through the periphery of the tip end of the blade.
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申请公布号 |
US4487550(A) |
申请公布日期 |
1984.12.11 |
申请号 |
US19830461424 |
申请日期 |
1983.01.27 |
申请人 |
THE UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE AIR FORCE |
发明人 |
HORVATH, RICHARD L.;HARRIS, ROBERT W. |
分类号 |
F01D5/18;F01D5/20;(IPC1-7):F01D5/18 |
主分类号 |
F01D5/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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